Atr

Front 1

In case of amber LOOP light on EWD.....

Back 1

Pilots turn off the faulty loop (to recover fire detection)

Front 2

What is the maximum permissible fuel imbalance between wings?

Back 2

730 kgs

Front 3

What will happen if the electrical supply to the digital control is lost in the automatic mode?

Back 3

Both outflow valves go to full CLOSE

Front 4

With the BAT switch OFF and no EXT PWR, what action is required to power the refuel/defuel system?

Back 4

Open the refuel/defuel panel door

Front 5

During normal landing gear operation:

Back 5

As soon as the gear is locked at its selected position, hydraulic operating pressure is released.

The main landing gear wheels are braked automatically as soon as the lever is selected up.

Front 6

The air conditioning air bleed valves are:

Back 6

Electrically controlled and pneumatically operated.

Front 7

What is the purpose of the "S" bend in the air intake duct?

Back 7

To provide uniform inlet flow to the compressor

Front 8

During an ATPCS engine Failure sequence, when does the ARM light extinguish?

Back 8

At the end of the autofeathering sequence.

Front 9

What is the minimum NP range (Propeller speed rotation), to insure that the ACW generator operates?

Back 9

66% - 70%

Front 10

What will happen to the Propeller brake if the blue hydraulic system pressure is lost during Hotel mode operation?

Back 10

Propeller brake will remain engaged

Front 11

The COMPT TEMP indicator displays:

Back 11

The compartment and duct temperature of the selected side.

Front 12

There is low pressure in the main green hydraulic pump:

Back 12

The crossfeed must be opened manually to restore the green pressure.

Front 13

The packs are located:

Back 13

One in each MLG fairing.

Front 14

To extinguish an engine fire:

Back 14

Pilots must pull the fire handle before using the extinguisher.

Front 15

.

Back 15

DC Bus 2 has failed

Front 16

Is it permitted to use the Propeller brake in flight?

Back 16

No

Front 17

A gate prevents PL angle reduction below flight idle in flight as soon as:

Back 17

Both main landing gear absorbers are released.

Front 18

Illumination of a SPLR light is an indication of what condition?

Back 18

The associated spoiler is not in the retracted position.

Front 19

With the ventilation panel set in the AUTO configuration, what will be the position of the ventilation valves in Hotel mode?

Back 19

The OVBD valve fully open, the U/F valve fully closed.

Front 20

Whenever the ICING AOA is illuminated, the aircraft is protected by an earlier stall threshold as follows:

Back 20

Both the stall alert and stick pusher thresholds are modified.

Front 21

The EMER BAT CHG fault light will illuminate when:

Back 21

Battery overheat occurs (automatic disconnection).

Front 22

White SQUIB light indicates...

Back 22

Squib is armed

Front 23

What does the absence of the green 'flow bar' in the XFEED push button indicate?

Back 23

The crossfeed valve is in transit, or a fault exists.

Front 24

The MFC system consists of:

Back 24

Two computers with four independent modules.

Front 25

With batteries only, when will both AC BUS 1 & AC BUS 2 be supplied?

Back 25

Never

Front 26

In normal operation, the electrical pump in each tank is used to:

Back 26

Start the engine, which pressurises the jet pump via its HMU HP fuel pump for subsequent pressurisation of the fuel system.

Front 27

If there is a fault with the De-/anti icing automatic mode, when should the de icing manual mode push button be selected to SLOW?

Back 27

When SAT is below -20°C ; causes a cycle length of 180 seconds

Front 28

In the APP mode, what must occur to capture and track the GS?

Back 28

The GS will capture automatically after LOC capture.

Front 29

In the event of an EEC fault, the fault light will illuminate steady once the PL is retarded below 52° (green range) and:

Back 29

The system automatically reverts to the manual mode which follows the HMU base law.

Front 30

To consider the great locked down, 3 green light must be illuminated on:

Back 30

Either overhead or the central instrument panels

Front 31

De icing

Back 31

Is active

Front 32

When condition levers are set from AUTO to 100% OVRD:

Back 32

Forces the Propeller Np to 100%

Front 33

The yellow symbol ADC2 on the PFD indicates?

Back 33

ADC1 is failed and information is now from ADC2

Front 34

Which flight control systems incorporate uncoupling mechanisms that permit separation into individual channels in the event of a jam?

Back 34

Pitch (elevators)

Front 35

During a go around, with the PWR MGT selected to T/O, to the ATPCS:

Back 35

Is armed for auto feathering only.

Front 36

A flashing 1A and 2A MFC FAULT light indicates:

Back 36

A self test is in progress.

Front 37

The aircraft is in IMC. Is it considered in icing conditions?

Back 37

Yes, because TAT is below +7°C

Front 38

Target speed is?

Back 38

240kt (magenta bug)

Front 39

Once the generator has started the engine, it switches to the generator mode when the engine speed accelerates past:

Back 39

NH 61.5%

Front 40

With the SBY BUS OVRD pb, where will the DC STBY BUS and the AC STBY BUS (via INV 1) be supplied from?

Back 40

The HOT EMER BAT Bus

Front 41

Flaps UNLK indicates:

Back 41

Flaps can not be extended at the selected value (and memory items must be applied)

Front 42

Can pilots perform and ILS approach using only the IESI?

Back 42

Yes, ILS tonight function and indications are available on IESI

Front 43

Where is the refuel/defuel panel located?

Back 43

Right hand MLG fairing.

Front 44

Is the fuel heated before the HP fuel pump to prevent icing?

Back 44

Yes by means of hot engine oil.

Front 45

ACW BUS 2 has failed

Back 45

TRU is lost

Front 46

Manual cancelation of TO INHIBIT is achieved by:

Back 46

Pressing the RCL pb

Front 47

What effect does a duct overheat (OVHT in TEMP SEL push button) have on pack valve operation?

Back 47

None

Front 48

What does the illumination of the red FLAP UNLK light indicate?

Back 48

Uncommanded retraction of the flaps when selected to 15° or more

Front 49

Operation of the emergency gear extension handle will mechanically unlock the gear and allow it to extend:

Back 49

Due to gravity, aerodynamic forces and a gas actuator.

Front 50

After take off, how is the ATPCS usually disarmed?

Back 50

When PWR MGT Selector is moved away from the TO position

Front 51

Roll trim control is performed using:

Back 51

The left handed balance tab

Front 52

What are the approx range limits for thr TCAS protected volume?

Back 52

20-45 seconds for TA , 15-35 seconds for RA

Front 53

For the AUX pump to run when the AUX pump pedestal switch is pressed:

Back 53

The BAT switch does not have to be switched ON

Front 54

370kg indicates

Back 54

The fuel mass in the left tank including feeder tank

Front 55

What power source supplies the refuel defuel panel?

Back 55

DC ground handling bus

Front 56

With the engines running, what does the illumination of a FEED LO PR light indicate?

Back 56

Low delivery pressure to the engine

Front 57

The aircraft is on the ground in fog conditions. Is an icing takeoff necessary (assume acceleration altitude is 500ft)

Back 57

No because SAT is above +5°C

Front 58

What is the expected reaction time of the pilot when a TCAS RA first occurs?

Back 58

5 seconds

Front 59

Pilots response to a "reversal" or "increase" RA should occur within:

Back 59

2.5 seconds

Front 60

The pressurization system is:

Back 60

In manual mode and cabin altitude target is 2600ft

Front 61

With the engines shutdown and the BAT switch off...

Back 61

The batteries remain connected to their respective HOT BAT BUSSES

Front 62

When is the COMPT temperature selector switch operative?

Back 62

In both manual and automatic mode.

Front 63

What do you set in the AUTO PRESS PANEL before each flight?

Back 63

Arrival airfield elevation

Front 64

Anti skid protection is operative at speeds over?

Back 64

10kts

Front 65

In flight "SGL CH" appears on the EWD:

Back 65

One channel of the PEC is lost

Front 66

At takeoff, what happens if an EEC FAULT occurs?

Back 66

Engine power remains virtually unchanged, the EEC FAULT light flashes and EEC de-selection is prohibited

Front 67

What provision is made to allow entry into the forward baggage compartment from the cockpit when oxygen is required?

Back 67

The supply hose on the observers mask is long enough for the purpose.

Front 68

Hydraulic pressure for the Propeller brake operation comes from which hydraulic system?

Back 68

The blue hydraulic system?

Front 69

For Air conditioning in Hotel mode the air is supplied via:

Back 69

The right engine air bleed valve and pack valve plus the left pack valve via the automatically opened cross feed valve

Front 70

Each MFC model processes data received from several systems and:

Back 70

The signals are taken into account by one or more modules, depending on the degree of reliability/safety required from the system.

Each model is supplied by two separate electrical sources (28VDC) primary and secondary.

Front 71

What happens when the pack FLOW push button is IN(HIGH illuminated)

Back 71

The pack valves operate at a higher regulated pressure(flow)

Front 72

With the N/100% rocker on the flight crew oxygen mask set to N the mask with deliver:

Back 72

A diluted oxygen flow only.

Front 73

Magenta box on the PFD indicates?

Back 73

The aircraft is below vertical profile computed by the FMS

Front 74

To obtain a correct pressure indication on the pressure gage located on the overheard panel:

Back 74

Electrical power (DC ESS BUS) is required

Front 75

With the aircraft on thr ground and the RH engine running at Max RPM, which main hydraulic pumps are powered?

Back 75

Both blue and green pumps

Front 76

When a pack overheated downstream of the compressor:

Back 76

The pack valve on the faulty side closes.

Front 77

Is the fuel crossfeed operation complete?

Back 77

No the left electro pump must be switched off

Front 78

The rudder spring tab function reduces the pilots effort on the rudder pedals:

Back 78

Whenever there is an airload.

Front 79

What will happen if the AP is engaged with a FD mode active?

Back 79

The AP will follow the active FD mode

Front 80

The services supplied by the BLUE hydraulic system are:

Back 80

NWS, flaps, spoilers, Propeller brake, emergency and parking brake.

Front 81

The power management Selector is used for?

Back 81

To change Torque and NP when the power levers are in the notch and condition levers are in AUTO.

Front 82

What VHF channels can pilots tune kn the IESI?

Back 82

VHF 1

Front 83

What have you lost?

Back 83

AHRS

Front 84

During landing when does the idle gate move rearward to allow the PL to be moved to GI?

Back 84

As soon as one landing gear absorber is compressed

Front 85

Assuming normal operation in flight, when are the DC EMER & DC ESS BUSSES connected to DC BUS 1 &/OR DC BUS 2?

Back 85

Always through the BAT CHG contactors and their respective HOT EMER OR HOT MAIN BAT BUS

Front 86

What is the purpose of the TLU?

Back 86

Limits rudder travel when flying at high speed

Front 87

Passenger Address system operation:

Back 87

Cockpit announcements have priority over cabin ones.

Front 88

If the No 1 Inverter fails:

Back 88

The AC BUS 1 OFF light will illuminate for 10sec and then extinguish and the INV fault light illuminates

Front 89

If the green system LO PR light illuminates with the green pump push button selected ON the cross feed valve will:

Back 89

Remain closed.

Front 90

Indicated Airspeed in 10sec will be ?

Back 90

229kts

Front 91

Which voice message will accompany a TCAS TA?

Back 91

Traffic traffic

Front 92

The aircraft is in normal non icing flight conditions. To safely retract the flap from 15 to 0 deg

Back 92

Speed must be above 122kt white bug

Front 93

The main pressure source for each engine of the hydraulic systems is?

Back 93

ACW electric pump

Front 94

The touch down protection function of the anti skid system will inhibit braking action for 5 seconds on low friction pavements or until wheel spin reaches:

Back 94

35kts

Front 95

The pneumatic outflow valve:

Back 95

Is slaved to the electronic pneumatic outflow valve in automatic mode.

Front 96

DU5 has failed.

Back 96

Automaric reconfig is performed by the system. Other view can be displayed via F/O switching "PFD/EWD/MFD". pb

Front 97

Amber ICING is flashing on the FMA

Back 97

Electronic ice detector detects ice accretion(De icing not selected ON yet)

Front 98

Aircraft in flight, ACW GEN 1 fails:

Back 98

ACW SVCE BUS is shed

Front 99

When is the ignition activated during the engine start sequence?

Back 99

When the CL is moves away from FUEL SO

Front 100

How high above takeoff elevation can the aircraft be operated before the automatic return feature is cancelled?

Back 100

3,500ft above take off field elevation

Front 101

What causes the illumination of the recirculation fan Fault Light?

Back 101

Fan RPM is too low and fan motor overheat.

Front 102

The NSW system will operate:

Back 102

Before takeoff as long as one landing gear indicated weight on wheels.

Front 103

The electric pump and the jet pumps are located:

Back 103

In the fuel tank feeder compartment

Front 104

In the event that both DC BUS 1 AND DC BUS 2 are lost. INV 1 will be supplied automatically by thr HOT MAIN BAT BUS or:

Back 104

Bu the HOT EMER BAT BUS in the OVRD configuration, or the TRU if selected ON.

Front 105

When is the NWS selected OFF on the CM1s lateral panel?

Back 105

Manually for towing and pushback

Front 106

With the DC BTC pb selected to NORM, when will the flow bar illuminate?

Back 106

During EXT PWR, HOTEL MODE OR single generator operation.

Front 107

Selection of the landing gear up.

Back 107

Will automatically apply the brakes until the gear is locked in the selected position.

Front 108

In the event of a thermal runaway of the MAIN BAT. The MAIN BAT CHG FAULT illuminates (BAT CHG contactor opens) and:

Back 108

The MAIN BAT supplies the HOT MAIN BAT BUS and DC ESS BUS is transfered to DC BUS 1.

Front 109

With one engine inoperative, are both sides of the Airframe de icing system supplied?

Back 109

Yes

Front 110

Each engine is equipped with:

Back 110

Two fire detection loops mounted in parallel

Front 111

Aircraft is on GND, PWR MGT set at TO, ATPCS push button ON. The ATPCS is armed when:

Back 111

Both PL are above 49° and both torques are above 46%

Front 112

In flight, with an extract fan failure. Avionics ventilation can be performed by selecting the exhaust mode push button to OVBD:

Back 112

Providing the OVBD valve switch is selected to AUTO.

Front 113

Which control surface linkages can be split?

Back 113

Elevators

Front 114

When are the power levers set to the RAMP?

Back 114

For go around.

Front 115

What will happen if the pitch wheels is operated with the AP engaged in the ALT mode?

Back 115

Nothing, pitch wheels inputs are inhibited in ALT mode.

Front 116

During the starting sequence of the left hand engine, the avionics vent extract fan will:

Back 116

Stop for 120 seconds and the exhaust mode FAULT light will illuminate.

Front 117

What is the function of the OVRD position for the BAT toggle switch?

Back 117

Overrides all automatic operation to ensure that the busses are supplied by their respective battery.

Front 118

Aircraft is in flight

Back 118

Pack 2 is supplying both compartments via the mixing chamber

Front 119

Can you land?

Back 119

Yes either indicator displaying 3 green lights is sufficient.

Front 120

The aux DC electrical hydraulic pump is part of which hydraulic system?

Back 120

The blue system

Front 121

Volume control of the two ceiling mounted cockpit speaker is:

Back 121

Adjusted by means of the associated volume control knobs..

Front 122

After discharging agent 1 into the left engine the indication you should see is:

Back 122

Agent 1 DISCH left engine and agent 2 DISCH right engine.

Front 123

When do the rolls spoilers start to operate?

Back 123

After and aileron deflection of 2.5°

Front 124

When do the rolls spoilers start to operate?

Back 124

After and aileron deflection of 2.5°

Front 125

The gust lock system acts on the:

Back 125

Roll and pitch control

Front 126

What do the two amber arrows indicate?

Back 126

The batteries are discharging

Front 127

The parking brake is:

Back 127

Available, because the brake accumulator is pressurized.

Front 128

With no external power available, will operation in Hotel mode provide power for the ACW system?

Back 128

No

Front 129

With no external power available, will operation in Hotel mode provide power for the ACW system?

Back 129

No

Front 130

Turning on the TRU:

Back 130

Supplies four busses without time limitations

Front 131

From where is the DC GND HDLG BUS powered?

Back 131

HOT MAIN BAT BUS OR DC SVCE BUS

Front 132

Fuel XFEED on the memo panel indicates:

Back 132

Fuel crossfeed is on

Front 133

Illumination of FAULT in the exhaust mode push button is an indication of:

Back 133

Extract fan failure

Front 134

With only the BAT switch ON, which battery powers the DC SBY BUS?

Back 134

The main battery.

Front 135

How is the air passing through the pack cooled when the Airspeed is above 150kts?

Back 135

Ram air

Front 136

What is the function of the EEC?

Back 136

To ensure minimum Propeller speed control(and therefore ACW gen operation) on the ground and at low power.

To provide uptime.power in case of engine failure during take off, and ensure, at a given engine rating, a constant PL position.

Front 137

After and engine fire, when does the red fire handle light extinguish?

Back 137

Only when the temperature detected by the loops drops below the warning threshold.

Front 138

The pneumatic system supplies air for?

Back 138

Air conditioning, pressurization, and ice protection.

Front 139

Airport met condition: expect icing conditions for takeoff. T/O data has been confirmed by the crew. Is this data correct?

Back 139

No because, ICING CONDITIONS, option is not selected and speed are computed for normal conditions.

Front 140

Under normal operation conditions, when is it possible to use the Propeller anti-icing system?

Back 140

Only when the NP is above 63%

Front 141

During Hotel mode operation, with the probes and windshield heating both switched ON, what items are heated?

Back 141

Static ports and STBY pitot.

Front 142

With the Propeller ant icing mode Selector push button selected to ON:

Back 142

Blades are heated for 20 seconds with a total cycle duration of 80 seconds.

Front 143

Following an Inverter failure the INV light illuminates and:

Back 143

The associated AC BUS is supplied by the other Inverter.

Front 144

What is the correct way to switch from automatic to manual pressurisation?

Back 144

Turn the MAN RAYE knob to 9'oclock position, select the MODE push button to MAN, and then operate the MAN RATE knob as required.

Front 145

When does the motive flow valve for the fuel feed jet pump open?

Back 145

When sufficient fuel pressure is available from the HMU.

When the associated electrical pump is running.

Front 146

What is the max usable fuel capacity of each tank.

Back 146

2500kg

Front 147

Which pack is the primary supplier of cockpit air?

Back 147

Left

Front 148

To climb from the cockpit through the emergency hatch....

Back 148

Steps are available.

Front 149

The main oxygen system is intended to provide oxygen for;

Back 149

The cockpit crew and the passengers.

Front 150

Which engine nacelles are equipped with a nacelles overheat system?

Back 150

The right hand only

Front 151

And engine fails in the cruise. Whay ATPCS function do you expect to occur?

Back 151

Nothing, ATPCS is not available during cruise.

Front 152

When does the red FUEL SO light in the CL illuminate?

Back 152

Whenever, the fire detection system operated. Provided the CL isn't at Fuel SO.

Front 153

In flight you see a master caution and flashing EEC FAULT light.

Back 153

You refer to the checklist, a flashing EEC should not be reset.

Front 154

The TO INHIBIT function is automatically cancelled when:

Back 154

The first leg of thr landing hear unlocks before retraction.

Front 155

Current vertical speed is?

Back 155

-900fpm

Front 156

When the DC starter/ generator is functioning as a starter during a battery start:

Back 156

It is electrically supplied from the HOT MAIN BAT BUS

Front 157

When the DC starter/ generator is functioning as a starter during a battery start:

Back 157

It is electrically supplied from the HOT MAIN BAT BUS

Front 158

When moving the CL from FTR TO AUTO

Back 158

The PEC is tested ("SGL CH" illuminates on EWD)

Front 159

In flight, PEC FAULT light illuminates

Back 159

Propeller speed is automatically protected (by the speed governer)

Front 160

With the engines shut down and BAT switch on:

Back 160

Allows EXT PWR operation, or a reduced DC supply.

Front 161

The stick pushed actuator is attached to:

Back 161

The LH control column

Front 162

What effect will testing the anti skid system with the brakes PARKED have on the brake system?

Back 162

No effect

Front 163

LNAV displayed on the FMA indicates?

Back 163

Pilot uses the FMS as primary navigation system

Front 164

How is a failed engine detected by the ATPCS?

Back 164

When one torque meter drops below 18%

Front 165

The illumination of the DISCH amber light indicates:

Back 165

The fire bottle has discharged (empty)

Front 166

Exhaust fault indicates:

Back 166

Extract fan is failed or over temperature

Front 167

The amber SINGLE SRC indicates?

Back 167

The autopilot is working with one source (ADC failure)

Front 168

How is the LP valve at the outlet of each fuel tank controlled?

Back 168

Electrically by the related fire handle

Front 169

How is the LP valve at the outlet of each fuel tank controlled?

Back 169

Electrically by the related fire handle

Front 170

To supply fuel to the left hand engine from the right hand fuel tank when both pumps are running you must:

Back 170

Open the crossfeed valve and select the left hand fuel pump push button off

Front 171

What does the appearance of an upward pointing arrow to the right of a TCAS instrument symbol indicate?

Back 171

The intruder is climbing

Front 172

When should the TCAS TA ONLY move be selected?

Back 172

In the event of an engine failure

Front 173

Can the ACW SVCE BUS be powered exclusively by an external AC supply?

Back 173

Yea but the flight attendant panel ACW GND SVCE BUS pb must be selected ON

Front 174

Amber APM fault light indicates:

Back 174

Aircraft Performance Monitoring (APM) system is faulty

Front 175

Illumination of the uptrim light during take off when one engine fails indicates what?

Back 175

The ATPCS has automatically increased torque on the live engine

Front 176

The services supplied by the GREEN hydraulic system are:

Back 176

Landing gear and normal brakes

Front 177

What effect will the illumination of a LO LVL light have on thr cross feed valve if it's open?

Back 177

The cross feed valve is automatically closed and inhibited

Hint 177

Hydraulics

Front 178

TLU LO SPEED indicates:

Back 178

Full rudder deflection is available

Front 179

When one of the PEC FAULT lights illuminates amber, what effect will selecting the relevant push button OFF have?

Back 179

The PEC is deactivated and NP blocked at 102% whenever power is sufficient

Front 180

If normal braking is lost anti skid is:

Back 180

Not available anymore

Front 181

18°C indicates:

Back 181

Cabin temp is 18°

Hint 181

Pressurization and air con

Front 182

In flight with one engine inop, which indication would be displayed on thr shutdown engines DC GEN pb?

Back 182

Amber fault is pb is depressed (in)

Front 183

Moving thr condition levers from FTR to AUTO:

Back 183

Unfeathers the Propeller

Front 184

When the ACW SVCE BUS is shed, what indications is given?

Back 184

SHED amber light on attendant panel ACW SVCE BUS pb

Front 185

When the ACW SVCE BUS is shed, what indications is given?

Back 185

SHED amber light on attendant panel ACW SVCE BUS pb

Front 186

When is the DUMP function available?

Back 186

It only works in AUTO PRESS mode

Front 187

When the pack valves are selected ON with bleed air available?

Back 187

Pack 1 valve open immediately, pack 2 valve opens after a 6 second delay

Front 188

When the weather radar is operating in thr weather detection mode (WX), which colour indicates the most intense rain?

Back 188

Magenta

Front 189

Which bleed supply is used at low engine power settings?

Back 189

HP comp

Front 190

When the emergency Selector on the flight crew oxygen mask is rotated in the direction of the arrow, the mask will deliver:

Back 190

A continously flow of 100% oxygen

Front 191

In flight with the exhaust mode push button selected to OVBD and the overboard valve control switch selected to AUTO:

Back 191

The extract fan is OFF, U/F valve is closed and the OVBD valve is partially open.

Front 192

With the aircraft of the ground BAT switch is OFF and the EXT PWR AVAIL light illuminated, what must be done to fully power the DC electrical system?

Back 192

Place the BAT switch to ON after the self test process is complete press the EXT PWR pb

Front 193

What is the maximum PLA available with the gust lock engaged (aircraft of ground)?

Back 193

A few degrees below flight idle

Front 194

Aircraft is in the cruise at FL250

Back 194

All pressurization parameters are normal

Front 195

Aircraft on ground, engines running, DC EXT power available and selected ON

Back 195

DC EXT PWR has priority over ENG DC GEN

Front 196

How many fire extinguisher bottles are there?

Back 196

Two common for both engines.

Front 197

How many fire extinguisher bottles are there?

Back 197

Two common for both engines.

Front 198

What effect will operation of just the top lever of the yaw trim switch have on the yaw trim actuator?

Back 198

No effect

Front 199

What aural warning is given in case of a fire or smoke warning?

Back 199

Continously repetitive chime

Front 200

Condition levers do what?

Back 200

Control the Propeller and the fuel opening closing.

Front 201

What does the pitch trim position indicator show?

Back 201

The travel of the right hand tab

Front 202

Assuming normal operation in flight, how is the constant frequency AC power obtained?

Back 202

From the DC busses through two inverters

Front 203

Rudder trim is achieved by means of an actuator which:

Back 203

Offsets the spring tab zero position

Front 204

The fluid for the hydraulic system is contained in:

Back 204

A single common tank which is divided into two compartments in the LH landing gear fairing

Front 205

In flight DC GEN 1 fails

Back 205

You expect the BTC to close automatically

Front 206

The MFC is operative as soon as:

Back 206

The battery is switched ON and the self test is completed

Front 207

You see ice on the "ICE EVIDENCE PROBE"

Back 207

You turn on ANTI ICING (if not done yet) and DE ICING (ENG, AIRFRAME)